1 / 40

Virtual-Aircraft Design & Control of TransCRuiser – S&C study with CEASIOM

Virtual-Aircraft Design & Control of TransCRuiser – S&C study with CEASIOM Arthur Rizzi 1 , P. Eliasson 2 , T. Grabowski 3 , J. Vos 4 1 Royal Institute of Technology (KTH), Stockholm, 100 44, Sweden 2 Swedish Defence Research Institute (FOI), Stockholm, 164 90, Sweden

clare-hinton
Download Presentation

Virtual-Aircraft Design & Control of TransCRuiser – S&C study with CEASIOM

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Virtual-Aircraft Design & Control of TransCRuiser– S&C study with CEASIOM Arthur Rizzi1, P. Eliasson2, T. Grabowski3, J. Vos4 1Royal Institute of Technology (KTH), Stockholm, 100 44, Sweden 2Swedish Defence Research Institute (FOI), Stockholm, 164 90, Sweden 3Warsaw University of Technology (WUT), 00-665 Warsaw, Poland 4CFS Engineering (CFSE), 1015 Lausanne Switzerland

  2. CEASIOM Design Tool – outcome of SimSAC Analyze/improve flight dynamics Specification & Design to Canard Configuration Creation Tabular Aero Data Comparison with WT data Prediction Flying Qualities - Low & transonic speeds Static stability – static margin: tradeoffs Dynamic stability – linear & nonlinear (flight simulator) Augmented Stability Demo Flight simulation Contents

  3. SimSAC EU-Project Partnership SimSAC:Simulating Aircraft Stability and Control Characteristics for Use in Conceptual Design EU FP 6 STREP project Project coordinator: Prof. A. Rizzi, KTH

  4. SimSAC Goal: Design Flight Control System Earlier • Compute Aerodyn Dataset • variable-fidelity CFD • predict flight dynamics • Use in conceptual design Aerodynamic Tools for S&C

  5. CEASIOM Design Tool Flight Dynamics

  6. TCR Design: SAAB Specification

  7. Original TCR: poor trim ability  large  ,  Different configurations investigated Wing further fore (design parameter) Three lifting surfaces All-moving canard (vary location & size) Design of wind tunnel model One moving surface for longitudinal control No engines Configuration Re-Design

  8. DesignChoice – Staticstabilitymargin Trimcondition M Static stable ac CG Dilemma ! Staticmargin L KngrowswithMa Response heavy at high speed CG = 38.3m

  9. Predict Flying Qualities: solve Flight Dyn Eqs • s – state vector (8) • A – inertia matrix • F – general forces Linearize ( stability derivatives...)

  10. FaeroInterpolation Process - Kriging Aero-data Data from source • Database constructed • DACE Kriging toolbox: • Linear base model, • Input & output scaled (0,1) • Manual choice corr. length Mach α

  11. Weight, Inertia & Balance Total Length 63.87 m Total Wingspan (bref) 44.66 m Total Canard Span 12.00 m Total Height 11.70 m Fuselage Diameter 3.70 m MAC 16.06/11.77 m, Wing reference area Sref = 489 m2, Reference point, moment x = 35.00 m, z = 0 m Center of gravity x = 38.33 m, z = 0 m W&B/ACBuilder: J.Munoz, S Ricci, ...

  12. Aero Data & Handling Qualities – Longitudinal Dynamics Cm(a) for zero canard deflection WT data Comparison Control authority: Canard stall

  13. Trim & Flying Qualities – low speed Trim Sensitivity small Phugoid a M.50 M.35 dCanard 120-180 m/s, 1km – 3km M 0.35 – 0.50 Short period

  14. Trim & Flying Qualities – transonic speed a Phugoid Short period dCanard Transonic dip M.65 M=1

  15. Flow Physics  transonic dip 220ms 250 270 286

  16. Linear & NonLinear Stability – Stick fixed Eigenvalues 276 m/s 10km, a = 0.5 All modes stable (barely ...) Flight simulation da = -0.3o: Slooowly damped da = -3.0o: See-saw pitchup ... Cobra manuver Wind gust - disturb α  small  large Time Histories a: AoA q: attitude

  17. Augmented Stability SAS OFF   SAS ON  

  18. Flying Qualities with Augmentation – low speed Phugoid Short Period ON OFF ON OFF ON Dutch Roll OFF

  19. CEASIOM proven useful ! Trim & static margin chosen correctly Good canard sizing & placement Verified by WT  no major pitfalls Stability Augmentation  good flying qualities Low-speed stick-fixed qualities improved Transonic disturbance damped Canard authority sufficient Allows concept designer to work with control tools to sort out: What can be fixed by control system What changes in configuration is needed CEASIOM lives on ! Community of users  Open software Visit www.ceasiom.com Join us ! Conclusions

  20. Thanks For Your Attention !

  21. CEASIOM Predicts T-tail Flutter Clamped node Stick Model: beam elements & lump masses Hor. Tail roll mode 3 4.3 Hz Fin bending mode 1 1.6 Hz V-g diagrams, sea-level

  22. Aircraft Motion: Non-Linear Dynamical System • s – state vector (8) • A – inertia matrix • F – general forces linearize

  23. WT Model

  24. Airspeed, Altitude & Mach number M.97

  25. Raymer volume coefficient ~ 0.1 lC = 28 m SC = 60 m2 MAC = 11.77 m S = 489 m2 cC ≈ 0.29 What if done by Handbook Method Handbook methods not applicable to unconventional configs. such as the TCR

  26. TCR Design: Specification Payload ‘Loose ideas’ to be Worked out: MTOW~ 180 t , R~ 10000 km , No Pax~ 200 Mc = 0.97

  27. Fused Aerodynamic Dataset Mach 

  28. Fused Aerodynamic Dataset Mach 

  29. Evolution of pitching moment & lift coefficients with Mach/speed Also breakpoints – no second-opinion – do we believe CFD ?? TCR - CFDsim - Machdependence

  30. Design Loops

  31. Design Process

  32. Flight Simulation – Transonic Cruise

  33. Baseline Design • InitialsizingwithSaab in-housemethod. • Baselinedesign: input for CEASIOM.

  34. CEASIOM Design Analysis: XML params

  35. TCR T-tail flutter Clamped node Stick Model: beam elements & lump masses Hor. Tail roll mode 3 4.3 Hz Fin bending mode 1 1.6 Hz • V-g diagrams, M∞=0.50, • sea-level

  36. Trim & longitudinal static stability Results from SDSA, for h=10 km and V = 240 m/s (M=0.8) TCR-C2 TCR-C17

  37. Trim & longitudinal static stability Results from SDSA, for h=10 km and V = 240 m/s (M=0.8) TCR-C17 TCR-C8

  38. Trim & longitudinal static stability Results from SDSA, for h=10 km and V = 240 m/s (M=0.8) distance W-C dC , static margin SC

  39. Construct Windtunnel Model • Exterior shape • - Export IGES • PoliMi designed • interior structure

More Related